Abstract: A ceramic matrix composite (“CMC”) center body may be positioned around an austenitic nickel-chromium-based superalloy attachment ring. The attachment ring may be integrally formed with a turbine engine case. The attachment ring may have a greater coefficient of thermal expansion than the center body. A plurality of pins may be inserted through apertures in the center body and coupled to the attachment ring. The pins may slide within the apertures, allowing the attachment ring to expand without applying a load on the center body.

Abstract: Aircraft landing gear assemblies and aircraft are provided. A landing gear assembly includes a main post and a light element cluster. The main post has a non-rotating portion and a rotatable steering portion. The light element cluster is associated with the non-rotating portion and includes at least two independently illuminating sections.

Abstract: An integrated power distribution, data network, and control architecture for a vehicle is provided that includes nodes distributed throughout the vehicle. Each node includes power distribution (PD) and data collection and distribution (DCD) components. The PD components receive electrical power from a source external to the node and distribute and control the electrical power supplied to active and passive electrical loads that are external to the node. The PD components include an electrical power input interface configured to receive an electrical power input from a source external to the node, and one or more power control modules. Each power control module can control the electrical power supplied to one or more electrical power output interfaces that supply power to the active and passive electrical loads. The DCD components receive data from data sources external to the node and transmit data to data consumers external to the node.

Abstract: A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

Abstract: An apparatus for controlling a hydraulically-actuated brake of an aircraft includes a brake control unit. The brake control unit is configured to receive a brake signal from an operator of the aircraft. A pump is in fluidic communication with a reservoir for holding hydraulic fluid and the brake for supplying the hydraulic fluid from the reservoir to the brake. An electric motor is in communication with the brake control unit and coupled to the pump to control pressure of the hydraulic fluid supplied by the pump in accordance with the brake signal.

Abstract: An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

Abstract: Aircraft landing gear assemblies and aircraft are provided. A landing gear assembly includes a main post and a light element cluster. The main post has a non-rotating portion and a rotatable steering portion. The light element cluster is associated with the non-rotating portion and includes at least two independently illuminating sections.

Abstract: Systems and methods are provided for monitoring, recording and/or reporting information about incidents that occur within proximity of an aircraft. When an incident monitoring mode is activated, external imagers of the aircraft begin recording of video images outside the aircraft in a temporary buffer as pre-event video data. Motion sensors that detect movement in the vicinity of the aircraft, and movement sensors that detect movement of the aircraft are also enabled. When a sensor detects a trigger event, an incident report file (IRF) is saved that includes the pre-event video data that is stored in the temporary buffer. Post-event video images are then recorded in the IRF as post-event video data until a condition occurs. Alarm signals that are perceptible outside the aircraft, and an incident report message can be generated and communicated to an external computer to indicate that an incident has occurred in proximity of the aircraft.

Abstract: An apparatus for controlling a hydraulically-actuated brake of an aircraft includes a brake control unit. The brake control unit is configured to receive a brake signal from an operator of the aircraft. A pump is in fluidic communication with a reservoir for holding hydraulic fluid and the brake for supplying the hydraulic fluid from the reservoir to the brake. An electric motor is in communication with the brake control unit and coupled to the pump to control pressure of the hydraulic fluid supplied by the pump in accordance with the brake signal.

Abstract: A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.

Abstract: An electric supercharger comprises a motor, for example a switched reluctance motor. The motor includes a stator assembly (101) comprising a plurality of pairs of windings (103A-C), each pair of windings (103A-C) comprising a first winding for forming a first pole and a second winding for forming a second, opposite, pole, each winding having an input termination (105) and an output termination (107). The terminations (105, 107) of each pair of windings (103A-C) are arranged such that the input terminations (105) for the first and second windings are located adjacent one another and the output terminations (107) of the first and second windings are located adjacent one another.

Abstract: An apparatus for supplying an internal combustion engine with a compressed air charge is disclosed. The apparatus includes a first compressing device, for example a turbocharger, and a second compressing device, for example an electric supercharger. The second compressing device is downstream of the first compressing device. A part, for example the bearing assembly, of the second compressing device is thermally shielded from the heat of the compressed air charge by a labyrinth seal.

Abstract: A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.

Abstract: Systems and aircraft for avoiding a collision between an obstacle an aircraft on a ground surface are provided. In some embodiments, the aircraft includes a wing and a stabilizer and a collision avoidance system includes proximity sensors, video imagers, and a display. Proximity sensors are disposed on the wing and the stabilizer. The respective proximity sensors are configured to transmit first and second obstacle detection signals. A first video imager is disposed on the wing and a second video imager is disposed on a rear portion of the aircraft. The respective video imagers are configured to generate video signals associated with the wing and with the stabilizer. The display is configured to generate video images of the regions in response to detection of objects in the regions.

Abstract: The disclosed embodiments relate to methods and systems for avoiding a collision between an obstacle and a vehicle, such as an aircraft, on a ground surface. A processor receives a detection signal from one of a plurality of proximity sensors. The detection signal indicates that the obstacle has been detected. In response to receiving the detection signal, a video image signal is transmitted from the processor to a display in the cockpit of the aircraft. The video image signal corresponds to a particular video imager that is associated with the particular proximity sensor that detected the obstacle. A video image, of a particular region around the aircraft that includes the obstacle is displayed on a display. In response to receiving the detection signal, the processor can also transmit an alert signal, and a brake activation signal to activate a braking system to prevent the aircraft from colliding with the obstacle.

Abstract: The disclosed embodiments relate to methods and systems for avoiding a collision between an aircraft and an obstacle when the aircraft is being moved on a ground surface via a ground vehicle. When a processor onboard the aircraft determines that the obstacle is located in proximity to the aircraft, the processor generates a warning generator signal, which causes an apparatus to communicate a warning signal that is perceptible to an operator of the ground vehicle to warn the operator of the obstacle.

Abstract: Recombinant microbial cells and methods for producing 5-hydroxytryptophan (5HTP) using such cells are described. More specifically, the recombinant microbial cell comprises an exogenous gene encoding an L-tryptophan hydroxylase, and means for providing tetrahydrobiopterin (THB). Related sequences and vectors for use in preparing such recombinant microbial cells are also described.

Abstract: Recombinant microbial cells and methods for producing melatonin and related compounds using such cells are described. More specifically, the recombinant microbial cell may comprise exogenous genes encoding one or more of an L-tryptophan hydroxylase, a 5-hydroxy-L-tryptophan decarboxylyase, a serotonin acetyltransferase, an acetylserotonin O-methyltransferase; an L-tryptophan decarboxy-lyase, and a tryptamine-5-hydroxylase, and means for providing tetrahydrobiopterin (THB). Related sequences and vectors for use in preparing such recombinant microbial cells are also described.

Abstract: The disclosed embodiments relate to methods and systems for identifying air traffic. A method is provided in which images from a camera positioned on the aircraft are processed via a processor. The processor uses data from the images to identify air traffic within a field of view of the camera and displays an indication of the position of the air traffic relative to the aircraft on a display to provide air traffic information. A system is also provided that includes an aircraft that includes a camera configured to provide image data within a field of view of the camera to a processor for processing the image data to identify air traffic within the field of view of the camera. The processor displays an icon representing the position of the air traffic within the field of view of the camera on a display to provide air traffic information.

Abstract: Composite coating materials comprising a hard carbide phase and a metallic binder that are resistant to molten metals such as aluminum are disclosed. The hard carbide phase of the composite coatings may comprise tungsten carbide, and the metallic binder may comprise a nickel-based alloy. A thin oxide layer comprising oxides of the binder metal may be provided on the surface of the composite coating. The composite coatings exhibit desirable non-wetting behavior when exposed to molten metals.